Summary
This document proposes the adoption of a new airworthiness directive (AD) that is applicable to certain Airbus Model A320 series airplanes. This proposal would require an initial inspection of fastener holes on certain outer frames of the fuselage to detect fatigue cracking, and modification of this area by cold expanding these holes and installing oversized fasteners. This proposal is prompted by a report from the manufacturer indicating that, during full-scale fatigue testing of the test article, fatigue cracking was detected in the area where the center fuselage joins the wing. The actions specified by the proposed AD are intended to prevent fatigue cracking and consequent reduced structural integrity of this area, which could lead to rapid depressurization of the fuselage.